Application of Practical Optimal Control Theory to the C-5A Load Improvement Control System (LICS)
Abstract
Practicalizing quadratic optimal control algorithms were used to design load relief systems for the C-5A, a large flexible aircraft. The predicted rms stresses at the wing root were reduced by more than 40 percent. Handling qualities or stability were not compromised. The control is realized with a gyro and three accelerometers affecting ailerons and elevator - two accelerometers more than an existing stability augmentation system. The quadratic performance index is defined to enforce good handling qualities and to limit the control system bandwidth.
Document Details
- Document Type
- Technical Report
- Publication Date
- Oct 01, 1973
- Accession Number
- AD0776297
Entities
People
- Albert J. Vandierendonck
- Charles R. Stone
- Michael D. Ward
Organizations
- Honeywell International, Inc.